US20050163606A1 - Centrifugal compressor with channel ring defined inlet recirculation channel - Google Patents
Centrifugal compressor with channel ring defined inlet recirculation channel Download PDFInfo
- Publication number
- US20050163606A1 US20050163606A1 US10/762,397 US76239704A US2005163606A1 US 20050163606 A1 US20050163606 A1 US 20050163606A1 US 76239704 A US76239704 A US 76239704A US 2005163606 A1 US2005163606 A1 US 2005163606A1
- Authority
- US
- United States
- Prior art keywords
- channel
- inlet
- impeller
- housing
- centrifugal compressor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
- F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
Definitions
- This invention relates to centrifugal compressors and to a channel ring defined inlet recirculation channel for such compressors.
- the present invention provides an integrated turbocharger inlet design that allows optimizing aerodynamic performance of a centrifugal compressor utilizing inlet air recirculation. Configuring the inlet components in an aerodynamic fixed configuration minimizes losses associated with prior designs of fixed geometry and costs associated with more complicated designs of variable geometry.
- the invention provides efficient compressor inlet air recirculation with a simple fixed channel system.
- three components, a compressor housing, an inlet member and a channel ring are interrelated to optimize the location, size and shape of a channel that joins a circumferential slot adjacent to the impeller with a circumferential opening preceding the impeller.
- FIG. 1 is a cross-sectional view of the compressor end of an engine turbocharger having a recirculation channel in accordance with the invention.
- FIG. 2 is an enlarged cross-sectional view of the recirculation channel portion of the embodiment of FIG. 1 .
- turbocharger 10 generally indicates a centrifugal compressor forming a portion of an engine turbocharger 11 .
- the turbocharger includes an exhaust driven turbine, not shown, connected with a drive shaft 12 for rotatably driving an impeller 14 of the compressor.
- the features of the invention could also apply to other centrifugal compressors whether or not connected with engines or turbochargers.
- the turbine, drive shaft and impeller are fixed together for rotation on a longitudinal axis 16 .
- the impeller 14 includes a plurality of vanes 18 , each having a leading edge 20 , a trailing edge 22 and an outer edge 24 .
- the compressor 10 further includes a compressor housing 26 , a diffuser 28 , an outlet scroll 30 , an inlet member 32 and a channel ring 34 .
- the compressor housing includes an annular wall 35 having an inlet portion 36 , an intermediate portion 38 , and an outlet portion 40 that forms a front wall for the diffuser.
- the outlet scroll 30 mounts around the diffuser 28 and the outlet portion 40 of the annular wall 35 to receive pressurized gas, such as air, from the diffuser 28 .
- the intermediate portion 38 extends for most of the length of and closely proximate to the outer edges 24 of the vanes 18 .
- the inlet member 32 is fixed to the inlet portion 36 of the housing wall and forms an inlet passage 42 of cylindrical or slightly frusto-conical configuration.
- the channel ring 34 has radial lugs or struts 44 that are fixed in slots 46 of the housing wall inlet portion 36 .
- other forms of attachment such as pins, could be utilized.
- the inner end of the inlet member 32 and the adjoining inlet end of the inlet portion 36 form an outwardly curved annular recess 48 in which an annular body 50 of the channel ring 34 is received.
- the body 50 of the channel ring 34 has an aerodynamic configuration which, in cross section of the illustrated embodiment, resembles an airfoil.
- An outer surface 52 of the ring 34 is curved in a manner similar to an upper surface of an aircraft wing having, for example, a rounded leading edge 54 connected with the outer surface 52 curving inward to a relatively sharp trailing edge 56 of the ring 34 .
- a connecting inner surface 58 extends linearly in a straight or slightly curved fashion from the inside of the rounded leading edge 54 to the sharp trailing edge 56 .
- the ring inner surface 58 extends longitudinally in relatively close alignment with the inlet passage 42 of the inlet member 32 and the interior of the intermediate portion 38 of the housing wall.
- the outer surface 52 of the channel ring is spaced inwardly from an opposing inner surface of the outwardly curved annular recess 48 to define an annular recirculation channel 60 .
- the channel 60 is configured with a smoothly diminishing annular cross section from a first slot 62 , at a forward end of the channel adjacent the inlet member, to a second slot 64 at a rearward end of the channel slightly beyond the inlet end of the impeller as defined by the leading edges 20 of the impeller vanes 18 .
- the thickness and longitudinal extent of the recirculation channel may be varied to obtain the desired amount and direction of recirculation air flow during operation of the compressor from the stall condition to the surge line of the pressure ratio map.
- the smaller cross section of the channel at the rearward second slot 64 allows flow into the impeller periphery to merge smoothly with the through flowing air stream.
- the larger cross section at the forward first slot 62 moderates air flow at this location to minimize the effect of reverse flow turbulence on the impeller blades leading edges.
- the radial support struts 44 are located in a zone of low momentum air flow near the opening of the first slot to minimize their effect upon the air flow in either forward or reverse directions.
- air enters the inlet member 32 and is directed into the impeller 14 , passing the leading edges 20 of at least some of the vanes 18 . Then inlet pressure differentials cause some of the air flow along the inner surface 58 of the channel ring to enter the second slot 64 and recirculate through the channel 60 and first slot 62 into the main inlet air stream upstream of the impeller.
- the recirculation flow decreases until the pressure differentials are reversed at higher mass flows. Then, some of the inlet air flow enters the first slot 62 , passes through the channel 60 to the second slot 64 and reenters the main air stream, passing through the impeller vanes 18 and supplementing the air flow through the impeller.
- the compressor air inlet system described provides both the functions of recirculating inlet air at low mass flows to move the surge line and increase operating range and bypassing inlet air at higher mass flows to increase the air flow passing through the impeller and being discharged from the compressor.
- the separate channel ring 34 allows the surfaces defining the recirculation channel 60 , as well as the inner surface 58 of the channel ring, to be fully machined or otherwise formed, prior to assembly, with smooth low friction surfaces and with close tolerances to minimize aerodynamic losses of the air flow in the channel.
- Mounting of the inlet member 32 and the channel ring radial struts, both, directly to the compressor housing also minimizes tolerance stack up, and positioning of the struts minimizes flow disturbances at the channel outlet slots.
- a minimum number of struts, such as four, is preferred for minimal flow interference.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
- This invention relates to centrifugal compressors and to a channel ring defined inlet recirculation channel for such compressors.
- It is known in the art relating to centrifugal compressors for air and other compressible gases that the operational range of pressure ratios of the compressor may be increased by providing bleed passages in the housing at suitable locations adjacent the impeller. This is particularly useful for engine turbocharger compressors, which are intended to operate over a wide range of rotational speeds under various conditions of engine speed, load and ambient pressure.
- In particular cases, air inlet recirculation has been proposed; however, the recirculation passages and the inlet and outlet slots have varied in cross-sectional area and smoothness and have not been designed for flow efficiency.
- The present invention provides an integrated turbocharger inlet design that allows optimizing aerodynamic performance of a centrifugal compressor utilizing inlet air recirculation. Configuring the inlet components in an aerodynamic fixed configuration minimizes losses associated with prior designs of fixed geometry and costs associated with more complicated designs of variable geometry.
- The invention provides efficient compressor inlet air recirculation with a simple fixed channel system. In a preferred embodiment, three components, a compressor housing, an inlet member and a channel ring are interrelated to optimize the location, size and shape of a channel that joins a circumferential slot adjacent to the impeller with a circumferential opening preceding the impeller.
- Use of the separate channel ring allows all surfaces of the channel to be accurately configured, by machining if required, to obtain an efficient flow channel configuration. Radial supports connecting the ring to the housing and inlet member are located near the channel inlet in an area of relatively low momentum air flow to prevent aerodynamic disturbances from adversely affecting the impeller during rotation at high speeds.
- These and other features and advantages of the invention will be more fully understood from the following description of certain specific embodiments of the invention taken together with the accompanying drawings.
-
FIG. 1 is a cross-sectional view of the compressor end of an engine turbocharger having a recirculation channel in accordance with the invention; and -
FIG. 2 is an enlarged cross-sectional view of the recirculation channel portion of the embodiment ofFIG. 1 . - Referring now to the drawings in detail,
numeral 10 generally indicates a centrifugal compressor forming a portion of anengine turbocharger 11. The turbocharger includes an exhaust driven turbine, not shown, connected with adrive shaft 12 for rotatably driving animpeller 14 of the compressor. However, the features of the invention could also apply to other centrifugal compressors whether or not connected with engines or turbochargers. - The turbine, drive shaft and impeller are fixed together for rotation on a
longitudinal axis 16. Theimpeller 14 includes a plurality ofvanes 18, each having a leadingedge 20, atrailing edge 22 and anouter edge 24. Thecompressor 10 further includes acompressor housing 26, adiffuser 28, an outlet scroll 30, aninlet member 32 and achannel ring 34. - The compressor housing includes an
annular wall 35 having aninlet portion 36, anintermediate portion 38, and anoutlet portion 40 that forms a front wall for the diffuser. The outlet scroll 30 mounts around thediffuser 28 and theoutlet portion 40 of theannular wall 35 to receive pressurized gas, such as air, from thediffuser 28. Theintermediate portion 38 extends for most of the length of and closely proximate to theouter edges 24 of thevanes 18. - The
inlet member 32 is fixed to theinlet portion 36 of the housing wall and forms aninlet passage 42 of cylindrical or slightly frusto-conical configuration. Thechannel ring 34 has radial lugs orstruts 44 that are fixed inslots 46 of the housingwall inlet portion 36. Alternatively, other forms of attachment, such as pins, could be utilized. - Surrounding the
channel ring 34, the inner end of theinlet member 32 and the adjoining inlet end of theinlet portion 36 form an outwardly curvedannular recess 48 in which anannular body 50 of thechannel ring 34 is received. Thebody 50 of thechannel ring 34 has an aerodynamic configuration which, in cross section of the illustrated embodiment, resembles an airfoil. - An
outer surface 52 of thering 34 is curved in a manner similar to an upper surface of an aircraft wing having, for example, a rounded leadingedge 54 connected with theouter surface 52 curving inward to a relatively sharptrailing edge 56 of thering 34. A connectinginner surface 58 extends linearly in a straight or slightly curved fashion from the inside of the rounded leadingedge 54 to the sharptrailing edge 56. The ringinner surface 58 extends longitudinally in relatively close alignment with theinlet passage 42 of theinlet member 32 and the interior of theintermediate portion 38 of the housing wall. - The
outer surface 52 of the channel ring is spaced inwardly from an opposing inner surface of the outwardly curvedannular recess 48 to define anannular recirculation channel 60. Thechannel 60 is configured with a smoothly diminishing annular cross section from afirst slot 62, at a forward end of the channel adjacent the inlet member, to asecond slot 64 at a rearward end of the channel slightly beyond the inlet end of the impeller as defined by theleading edges 20 of theimpeller vanes 18. - The thickness and longitudinal extent of the recirculation channel may be varied to obtain the desired amount and direction of recirculation air flow during operation of the compressor from the stall condition to the surge line of the pressure ratio map. The smaller cross section of the channel at the rearward
second slot 64 allows flow into the impeller periphery to merge smoothly with the through flowing air stream. The larger cross section at the forwardfirst slot 62 moderates air flow at this location to minimize the effect of reverse flow turbulence on the impeller blades leading edges. Theradial support struts 44 are located in a zone of low momentum air flow near the opening of the first slot to minimize their effect upon the air flow in either forward or reverse directions. - In operation of the compressor with low mass air flow, air enters the
inlet member 32 and is directed into theimpeller 14, passing the leadingedges 20 of at least some of thevanes 18. Then inlet pressure differentials cause some of the air flow along theinner surface 58 of the channel ring to enter thesecond slot 64 and recirculate through thechannel 60 andfirst slot 62 into the main inlet air stream upstream of the impeller. - As the impeller speed increases, the recirculation flow decreases until the pressure differentials are reversed at higher mass flows. Then, some of the inlet air flow enters the
first slot 62, passes through thechannel 60 to thesecond slot 64 and reenters the main air stream, passing through theimpeller vanes 18 and supplementing the air flow through the impeller. - The compressor air inlet system described provides both the functions of recirculating inlet air at low mass flows to move the surge line and increase operating range and bypassing inlet air at higher mass flows to increase the air flow passing through the impeller and being discharged from the compressor.
- Use of the
separate channel ring 34 allows the surfaces defining therecirculation channel 60, as well as theinner surface 58 of the channel ring, to be fully machined or otherwise formed, prior to assembly, with smooth low friction surfaces and with close tolerances to minimize aerodynamic losses of the air flow in the channel. Mounting of theinlet member 32 and the channel ring radial struts, both, directly to the compressor housing also minimizes tolerance stack up, and positioning of the struts minimizes flow disturbances at the channel outlet slots. A minimum number of struts, such as four, is preferred for minimal flow interference. These features all contribute to the efficiency of the low loss channel design, the configuration of which may be varied as needed to match various compressor configurations. - In summary, the invention emphasizes the following features:
- a compact, fixed geometry;
- a simple, cost-effective construction including profiled recirculation channel surfaces and slot openings;
- slots easily modified for differing impeller geometries;
- inner channel geometry minimizing fluid momentum loss to increase compressor efficiency; and
- minimal channel obstructions away from the
rear impeller slot 64 to prevent aero-mechanical excitation of the impeller at higher air flows. - While the invention has been described by reference to certain preferred embodiments, it should be understood that numerous changes could be made within the spirit and scope of the inventive concepts described. Accordingly, it is intended that the invention not be limited to the disclosed embodiments, but that it have the full scope permitted by the language of the following claims.
Claims (9)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/762,397 US6945748B2 (en) | 2004-01-22 | 2004-01-22 | Centrifugal compressor with channel ring defined inlet recirculation channel |
EP05000025A EP1557568A3 (en) | 2004-01-22 | 2005-01-03 | Centrifugal compressor with inlet recirculation channel |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/762,397 US6945748B2 (en) | 2004-01-22 | 2004-01-22 | Centrifugal compressor with channel ring defined inlet recirculation channel |
Publications (2)
Publication Number | Publication Date |
---|---|
US20050163606A1 true US20050163606A1 (en) | 2005-07-28 |
US6945748B2 US6945748B2 (en) | 2005-09-20 |
Family
ID=34634594
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/762,397 Expired - Fee Related US6945748B2 (en) | 2004-01-22 | 2004-01-22 | Centrifugal compressor with channel ring defined inlet recirculation channel |
Country Status (2)
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US (1) | US6945748B2 (en) |
EP (1) | EP1557568A3 (en) |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20050008484A1 (en) * | 2003-04-30 | 2005-01-13 | Bahram Nikpour | Compressor |
US20050196272A1 (en) * | 2004-02-21 | 2005-09-08 | Bahram Nikpour | Compressor |
US20070271921A1 (en) * | 2006-05-24 | 2007-11-29 | Honeywell International, Inc. | Inclined rib ported shroud compressor housing |
US20100061840A1 (en) * | 2008-09-11 | 2010-03-11 | Ronren Gu | Compressor with variable-geometry ported shroud |
WO2013191937A1 (en) * | 2012-06-18 | 2013-12-27 | Borgwarner Inc. | Compressor cover for turbochargers |
US20150198163A1 (en) * | 2014-01-15 | 2015-07-16 | Honeywell International Inc. | Turbocharger With Twin Parallel Compressor Impellers And Having Center Housing Features For Conditioning Flow In The Rear Impeller |
CN105332929A (en) * | 2015-12-11 | 2016-02-17 | 中国北方发动机研究所(天津) | Bypass recycling centrifugal air compressor with reverse guide blade |
US20160131145A1 (en) * | 2014-11-10 | 2016-05-12 | Honeywell International Inc. | Adjustable-trim centrifugal compressor with ported shroud, and turbocharger having same |
US9482240B2 (en) | 2013-07-31 | 2016-11-01 | Honeywell International Inc. | Compressor housing assembly for a turbocharger |
CN107476878A (en) * | 2016-06-08 | 2017-12-15 | 通用汽车环球科技运作有限责任公司 | Turbocharger variable inlet pipe |
US20180045214A1 (en) * | 2016-08-15 | 2018-02-15 | Borgwarner, Inc. | Compressor wheel, method of making the same, and turbocharger including the same |
US10378557B2 (en) | 2013-12-06 | 2019-08-13 | Borgwarner Inc. | Reduced noise compressor recirculation |
Families Citing this family (18)
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US20050123394A1 (en) * | 2003-12-03 | 2005-06-09 | Mcardle Nathan J. | Compressor diffuser |
EP1571348A3 (en) * | 2004-03-05 | 2008-12-24 | AWECO APPLIANCE SYSTEMS GmbH & Co. KG | Centrifugal pump |
US7698894B2 (en) * | 2006-05-22 | 2010-04-20 | International Engine Intellectual Property Company, Llc | Engine intake air compressor and method |
US8241005B2 (en) * | 2008-10-16 | 2012-08-14 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine centrifugal impeller |
US20100159816A1 (en) * | 2008-12-23 | 2010-06-24 | International Business Machines Corporation | Converging segments cooling |
US20100178164A1 (en) | 2009-01-15 | 2010-07-15 | General Electric Company | System and method for turbocharging an engine |
DE102009052162B4 (en) * | 2009-11-06 | 2016-04-14 | Mtu Friedrichshafen Gmbh | Compressor arrangement and method for producing such |
DE102009054771A1 (en) * | 2009-12-16 | 2011-06-22 | Piller Industrieventilatoren GmbH, 37186 | Turbo compressor |
EP2951440B1 (en) | 2013-01-31 | 2019-07-31 | Danfoss A/S | Centrifugal compressor with extended operating range |
US20150377240A1 (en) | 2014-06-27 | 2015-12-31 | Electro-Motive Diesel Inc. | Turbocharger having vaned compressor inlet recirculation passage |
EP3165775B1 (en) | 2014-07-03 | 2019-09-04 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Compressor cover, centrifugal compressor, and supercharger, and compressor cover manufacturing method |
US10267214B2 (en) * | 2014-09-29 | 2019-04-23 | Progress Rail Locomotive Inc. | Compressor inlet recirculation system for a turbocharger |
WO2016151689A1 (en) * | 2015-03-20 | 2016-09-29 | 三菱重工業株式会社 | Centrifugal compressor and supercharger comprising same |
US10962016B2 (en) | 2016-02-04 | 2021-03-30 | Danfoss A/S | Active surge control in centrifugal compressors using microjet injection |
CN115559913A (en) | 2018-01-19 | 2023-01-03 | 概创机械设计有限责任公司 | Turbine with separate collectors |
JP6848890B2 (en) * | 2018-01-23 | 2021-03-24 | 株式会社豊田自動織機 | Turbocharger |
DE102019115011A1 (en) * | 2019-06-04 | 2020-12-10 | Borgwarner Inc. | Compressor with inlet insert and return duct |
CN112983846A (en) | 2019-12-02 | 2021-06-18 | 开利公司 | Centrifugal compressor and method for operating a centrifugal compressor |
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US4248566A (en) * | 1978-10-06 | 1981-02-03 | General Motors Corporation | Dual function compressor bleed |
US4743161A (en) * | 1985-12-24 | 1988-05-10 | Holset Engineering Company Limited | Compressors |
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Cited By (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20050008484A1 (en) * | 2003-04-30 | 2005-01-13 | Bahram Nikpour | Compressor |
US7229243B2 (en) * | 2003-04-30 | 2007-06-12 | Holset Engineering Company, Limited | Compressor |
US20050196272A1 (en) * | 2004-02-21 | 2005-09-08 | Bahram Nikpour | Compressor |
US20080232959A1 (en) * | 2004-02-21 | 2008-09-25 | Bahram Nikpour | Compressor |
US7686586B2 (en) | 2004-02-21 | 2010-03-30 | Holset Engineering Company, Limited | Compressor |
US20070271921A1 (en) * | 2006-05-24 | 2007-11-29 | Honeywell International, Inc. | Inclined rib ported shroud compressor housing |
US7475539B2 (en) * | 2006-05-24 | 2009-01-13 | Honeywell International, Inc. | Inclined rib ported shroud compressor housing |
US20100061840A1 (en) * | 2008-09-11 | 2010-03-11 | Ronren Gu | Compressor with variable-geometry ported shroud |
US8061974B2 (en) * | 2008-09-11 | 2011-11-22 | Honeywell International Inc. | Compressor with variable-geometry ported shroud |
CN104321513A (en) * | 2012-06-18 | 2015-01-28 | 博格华纳公司 | Compressor cover for turbochargers |
WO2013191937A1 (en) * | 2012-06-18 | 2013-12-27 | Borgwarner Inc. | Compressor cover for turbochargers |
US9482240B2 (en) | 2013-07-31 | 2016-11-01 | Honeywell International Inc. | Compressor housing assembly for a turbocharger |
US10378557B2 (en) | 2013-12-06 | 2019-08-13 | Borgwarner Inc. | Reduced noise compressor recirculation |
US20150198163A1 (en) * | 2014-01-15 | 2015-07-16 | Honeywell International Inc. | Turbocharger With Twin Parallel Compressor Impellers And Having Center Housing Features For Conditioning Flow In The Rear Impeller |
US20160131145A1 (en) * | 2014-11-10 | 2016-05-12 | Honeywell International Inc. | Adjustable-trim centrifugal compressor with ported shroud, and turbocharger having same |
US9719518B2 (en) * | 2014-11-10 | 2017-08-01 | Honeywell International Inc. | Adjustable-trim centrifugal compressor with ported shroud, and turbocharger having same |
CN105332929A (en) * | 2015-12-11 | 2016-02-17 | 中国北方发动机研究所(天津) | Bypass recycling centrifugal air compressor with reverse guide blade |
CN107476878A (en) * | 2016-06-08 | 2017-12-15 | 通用汽车环球科技运作有限责任公司 | Turbocharger variable inlet pipe |
US20180045214A1 (en) * | 2016-08-15 | 2018-02-15 | Borgwarner, Inc. | Compressor wheel, method of making the same, and turbocharger including the same |
US10436211B2 (en) * | 2016-08-15 | 2019-10-08 | Borgwarner Inc. | Compressor wheel, method of making the same, and turbocharger including the same |
Also Published As
Publication number | Publication date |
---|---|
US6945748B2 (en) | 2005-09-20 |
EP1557568A2 (en) | 2005-07-27 |
EP1557568A3 (en) | 2012-06-06 |
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